US 12,404,809 B2
Heating turbomachine for a fuel-conditioning system configured to supply an aircraft turboshaft engine with fuel from a cryogenic tank
Nicolas Claude Parmentier, Moissy-Cramayel (FR); and Samer Maalouf, Moissy-Cramayel (FR)
Assigned to SAFRAN, Paris (FR)
Appl. No. 18/836,448
Filed by SAFRAN, Paris (FR)
PCT Filed Feb. 9, 2023, PCT No. PCT/EP2023/053217
§ 371(c)(1), (2) Date Aug. 7, 2024,
PCT Pub. No. WO2023/152232, PCT Pub. Date Aug. 17, 2023.
Claims priority of application No. 2201236 (FR), filed on Feb. 11, 2022.
Prior Publication US 2025/0172093 A1, May 29, 2025
Int. Cl. F02C 7/224 (2006.01); F02C 3/22 (2006.01)
CPC F02C 7/224 (2013.01) [F02C 3/22 (2013.01); F05D 2220/323 (2013.01); F05D 2260/213 (2013.01)] 10 Claims
OG exemplary drawing
 
1. An assembly comprising a cryogenic tank, an aircraft turboshaft engine and a fuel-conditioning system connecting the cryogenic tank to the aircraft turboshaft engine, the fuel-conditioning system comprising:
a fuel circuit configured to connect the cryogenic tank to the aircraft turboshaft engine, and
a heating turbomachine comprising:
a compressor configured to be supplied by an air flow from an air inlet,
a turbine connected to the compressor by a turbomachine shaft, and
a combustion chamber configured to be supplied with the air flow from the compressor and by a fuel flow, the combustion chamber being configured to discharge an exhaust air flow loaded with heat energy and to rotate the turbine,
at least one fluid circuit in which a heat-transfer fluid circulates from upstream to downstream,
at least one post-combustion heat exchanger, which is mounted in the at least one fluid circuit and is configured to extract the heat energy from the exhaust air flow between the combustion chamber and the turbine, and
at least one exhaust heat exchanger which is mounted in the at least one fluid circuit and is configured to heat the heat-transfer fluid from the heat energy extracted from the exhaust air flow at an outlet of the turbine,
the heating turbomachine being configured to heat a fuel stream circulating through the fuel-conditioning system from the heat energy extracted by the heat transfer fluid, the combustion chamber being supplied by the fuel flow from the fuel-conditioning system.
 
10. A method for heating the heat-transfer fluid by means of the heating turbomachine in the assembly according to claim 1, the heat-transfer fluid circulating from the upstream to the downstream in the at least one fluid circuit, the method comprising the steps:
supplying the compressor with the air flow,
supplying the combustion chamber with the air flow from the compressor and with the fuel flow, the combustion chamber discharging the exhaust air flow loaded with the heat energy in order to rotate the turbine, and
heating the heat-transfer fluid in the at least one post-combustion heat exchanger using the heat energy extracted from the exhaust air flow at an outlet of the combustion chamber.